Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(goe403-il) GOE 403 AIRFOIL | Gottingen 403 airfoil Max thickness 6.7% at 29.9% chord Max camber 4.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe403-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe403-il | 50,000 | 9 | 42.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe403-il | 50,000 | 5 | 41.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe403-il | 100,000 | 9 | 59.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe403-il | 100,000 | 5 | 57.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe403-il | 200,000 | 9 | 75.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe403-il | 200,000 | 5 | 73 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe403-il | 500,000 | 9 | 98.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe403-il | 500,000 | 5 | 92.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe403-il | 1,000,000 | 9 | 116.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe403-il | 1,000,000 | 5 | 107.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||